A Laval nozzle exhaust air from a large reservoir into ambient conditions (Ps = 100 kPa) and (Mexit = 2). What reservoir pressure (Pt) that would cause a normal shock to form at the exit * %3D %3D a. Pt = 510.8 kPa 1108 kPn

A Laval nozzle exhaust air from a large reservoir into ambient conditions (Ps = 100 kPa) and (Mexit = 2). What reservoir pressure (Pt) that would cause a normal shock to form at the exit * %3D %3D a. Pt = 510.8 kPa 1108 kPn

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: of discharge from convergent-dioergent nozle expanding from 8 bar and 210°C to 0.1 bar. When the,…

A: The answer is in the next steps

Q: The velocity of flow after a normal shock wave when (Tx= ,315 K, vx= 555 ms-1) 275.7 ms-1 O 396.1…

Q: 3. Calculate the air mass flow rate, Fuel-to air ratio , Exhaust gas speed, and maximum engine…

A: Flight speed vF=250 msecT0=290 K.P0=.75 barThrust force T=3.2 kNSpecific fuel consumption(sfc)=.75…

Q: A double-tank system in Fig. has two identical convergingnozzles of 1-in2 throat area. Tank 1 is…

A: Given data: Initial temperature, T0 = 5200R Pressure at point 1, P1 = 100 lbf/in2 Throat area of…

Q: It can be shown that the optimum jet speed ratio for the two streams in a KE. Explain why the…

A: the conditions to which the optimum fan pressure ratio has been better in this case, VjcVjhop=ηKE It…

Q: A high-pressure air reservoir is connected to the inlet of a convergent-divergent nozzle with an…

A: Nozzle : It is a device which having reducing cross sectional area from entrance to exit. This…

Q: Example 14.3 A supersonic two-dimensional inlet is to be operate at M 3.0. Two possibilities will be…

Q: rne delivéred procating air co e and 10 cm sta rolumetric effic

A: given:volume delivered =0.42×103m3bore diameter d=8cmstroke length=10cm

Q: Air from a reservoir at 200kPa and 350K is expanded through a convergent-divergent nozzle of throat…

A: reservoir pressure = 200 kPa reservoir temperature = 350 K throat area =0.2 m2 exit area = 0.8 m2…

Q: Stagnation level S JA C d, arən=Zg(B-y) C, D 0=xenhe="a v =-apay=VC, d, Datum E 2B 2B

A: A hydroelectric dam is one of the critical pieces of a hydroelectric office. A dam is a huge,…

Q: Example (5): Gases expand in a propulsion nozzle from 3.5 bar and 425 C down to a back pressure of…

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: In the figure below, M1 = 3.0 and A1 = 2.0ft?. If the fluid is carbon monoxide and the shock occurs…

Q: equal to 3.0. Find Me, Pe, and the loss in stagnation pressure (Poi - Poe). Repeat for a ock at the…

A: Given Image,

Q: Air from a reservoir at 200kPa and 350K is expanded through a convergent-divergent nozzle of throat…

A: Given : Reservoir pressure = 200 kPa Reservoir temperature = 350 K Throat area of nozzle = 0.2 m2…

Q: If 쏘= 1.296, P2 = 387kPa. The static exit pressure P2 equal to %3D %3D A. a. P2 = 510 kPa %3D Shock…

Q: Rafe Air is contained in an insulated rigid column at 20 degree Celsius and 200 kPA. A paddle wheel…

A: The temperature of the air,T1=20oC=293 K. The pressure of the air,P1=200 kPa The paddle work on the…

Q: propagates at à speed of normal shock wa m/s down a pipe thát is filled with hydrogen. The hydrogen…

Q: In a nozzle, steam enters at T = 673.15 K and P = 800,000 Pa while u = 10 m/s. It exits at T =…

A: What is the ratio of the inlet and outlet diameters (D1/D2)?

Q: Air is supplied to a C-D nozzle from a large reservoir where the temperature is To = 400 K, as shown…

A: Given:Temperature T0 = 400 K Velocity at inlet section V1 = 120 m/sFor air:Cp = 1005R = 287 y = 1.4

Q: The stagnation pressure across ,a normal shock wave is always poy ≥ pox O poy = pox O poy pox O

A: Option: is correct poy < pox Because across the normal shock wave the stagnation pressure…

Q: The stagnation density after the shock (px= 55 kPa, Tx= 335 K, vx= 525 ms-1),

Q: An adiabatic, SSSF, single inflow/outflow nozzle has negligible kinetic energy on the inflow, and…

Q: An engine is being designed to cruise at an altitude of 20,000 ft. The compressor fan face should…

A: given data; ⇒mach number (Ma)=0.8⇒mass flow (m)=70.30lbm/s=31.88kg/s⇒lets take at atmospheric…

Q: Air with stagnation pressure of 800 kPa and temperature of 100⁰C ,is expanded isentropically to the…

Q: 5. Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless…

A: Give:- Pox = 600Kpa, Tox = 530K, At = 5 cm2, Ae = 12.5 cm2, Pe = 300Kpa. To Find:- Pb,e = ?

Q: 5. Combustion gases with k=1.35, Cp=1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation pressure…

A: Given Data: k = 1.35Cp=1107 J/kg-KR=287 J/kg-Kps=390 kPaTs=1150 Kpstatic=100 kPaM=1ηts=80% To…

Q: Q3: Supersonic divergent duct with Mach inlet 3 and exit Mach number equal to 0.4. Normal shock wave…

A: Given, Inlet Mach number, M1=3AiAi*=4.2346Outlet Mach number,M2=0.4AeAe*=1.5901AlsoAiAe=0.5 (Given…

Q: 2. Determine the back pressure necessary for a normal shock to appear at the exit of a…

A: Given:From one-dimensional isentropic compressible functions of an ideal gas table,For the given air…

Q: The stagnation pressure after the normal shock wave in a diverging nozzle (pi= 170 kPa, ,Mi= 2.4,…

Q: Under expansion flow in convergent- -10 divergent nozzle accurse with exit supersonic flow when Pb <…

A: Option is False

Q: Air flows isentropically. Using the below table and find the divergent exit temperature, and…

A: Write the given data. At entry,Ma=0.4A=0.2 m2P=1 MPa T=300 KAt exit,Ma=2

Q: Ex 1 // sentropic flow of air in convergent nozzle is supplied from a large reservoir in which the…

Q: 9.9 Combustion gases with cp = 1148 J/kg K and gas constant R = 287 J/kgK enter the stator of a…

A: A dimensionless quantity in fluid mechanics which is the ratio between the velocity of the fluid…

Q: Select one limitation of the use of the Bernoulli Equation? А. Must consider frictional effects for…

A: GIVEN- TOPIC -FLUID MECHANICS DETERMINE CORRECT OPTION OF LIMITATIONS OF USE OF…

Q: Q8: Two engine inlets, one a straight tube, the other a converging-diverging diffuser. Both with M =…

Q: A normal shock wave occur at the exit of converging nozzle. Oxygen inlet with 2.8 Mach, the nozzle…

Question

A Laval nozzle exhaust air from a large reservoir into ambient conditions
(Ps
= 100 kPa) and (Mexit = 2). What reservoir pressure (Pt) that would cause a normal shock
%3D
to form at the exit *
a. Pt = 510.8 kPa
O d. Pt = 110.8 kPa
c. Pt = 193.7 kPa
%3D
O b. Pt = 173.7 kPa

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Result

VIEW

Step by step

Solved in 3 steps with 2 images

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

One Question more for the solution above : Calculate the location of the normal shock inside the nozzle and the exit flow properties. Thanks :)
Q1> Air at 30 C and 101 Pa is drawn through a covergent-divergent nczze with thrcat area 0.025 m² and exit area 0.0724 m², discharging into a large vacuun tank. Determíne the conditions (a) upstream and b) dourstrearm of a normal shock which is positioned at the nozzie exit
Please solve asap!!!!!!??:;
02: Air flows isentropically through converging nozzle which has a throat of The stagnation conditions are 130 kpa and 380 K. Find the exit pressure and flow rate if the atmospheric pressure is: (a) 88 kpa. (b) 40 kpa. (Take: K = 1.4, C, =1005 J/kg.k and R = 287 J/kg.k for air)
A gas turbine stage develops 3.4MW for a mass flow of 27 kg/sec. The stagnation pressure and temperature at the stage entry are 772 kPa and 100OK. The axial velocity is constant throughout the stage, the gases entering and leaving the stage without any absolute whirl. At the nozzle exit, the static pressure is 480kPa and the flow direction is at 72°. Let C,=1.148, R=0.287. Determine the following: a) the axial velocity, b) the degree of reaction for the stage given that the entropy increase in the nozzles is 13 J/(kg °C),
A converging-diverging nozzle with an exit-to-sonic area ratio of Ae/A = 47, exhausts air from a high-pressure reservoir (T, = 270 K) to the back plane, where the pressure is fixed at p, = 1 atm [abs). The test section area is Aa = 0.06 m? and the reservoir has a volume of 50 m. a) Assume that the test is located immediately upstream of the exit and that the flow up to the exit is isentropic, what is the minimum stagnation pressure under which the tunnel will start? b) What is the test section pressure under these conditions?
I need the answer as soon as possible
A radial flow reaction turbine has the following characteristics: Circumferential area at entrance and exit: Ag = 258 cm² ,Ac2 = 180 cm² ; Q = 0.1n7 = 0.82 ,r, = 25 cm, r3 - 12.5 cm, B, = 140°, Bz = 155°, az = 90°, 0, = 0.75, and nwyd = 92 % . Assume shockless entrance of water to blade. Find: (a) The rotative speed under these conditions, in rpm (b) The hydraulic Torque, in k) The Brake Power in kW (c) (d) the coefficient of velocity c, at entrance to blade (e) The net Head, in m. (f) Draw the velocity diagram and label.
ASAP
Need asap in 30 min i will give like
new chapter of me study today